Title :
Application of predictive guidance to reentry vehicle
Author :
Zheng, Liwei ; Jing, Wuxing
Author_Institution :
Dept. of Aerosp. Eng., Harbin Inst. of Technol.
Abstract :
A predictive guidance method for reentry vehicle is investigated, which has capability of handling a wider variety of reentry condition. The optimal correction of vehicle´s velocity to attack the stationary target on the Earth´s surface is calculated by resolving Gauss equation and Newton iteration equation. To achieve this goal, the required aerodynamic forces are derived by adjusting vehicle´s attack angle and side-slip angle. Simulation results show that the presented algorithm can satisfy the requirement of landing error. Moreover, it is easy of implementation and capable of tolerating atmospheric disturbances as well as navigation errors
Keywords :
Newton method; aerospace control; position control; predictive control; Gauss equation; Newton iteration equation; attack angle; landing error requirement; predictive guidance; reentry vehicle; side-slip angle; stationary target; Aerodynamics; Equations; Gaussian processes; Land vehicles; Military computing; Navigation; Prediction algorithms; Predictive models; Road vehicles; Trajectory;
Conference_Titel :
Systems and Control in Aerospace and Astronautics, 2006. ISSCAA 2006. 1st International Symposium on
Conference_Location :
Harbin
Print_ISBN :
0-7803-9395-3
DOI :
10.1109/ISSCAA.2006.1627421
